Propulsion unit



Feb. 13, 1962 w. F. MOORE PROPULSION UNIT 5 Sheets-Sheet 1 Filed June10, 1960 FIG. I

INVENTOR. WENDELL F. MOORE Q24, M, W wa- ATTORNEKS Feb. 13, 1962 w. F.MOORE PROPULSION UNIT 5 Sheets-Sheet 2 Filed June 10. 1960 INVENTOR.WENDELL F. MOORE dial-4. M, ATTORNEY) Feb. 13, 1962 w. F. MOOREPROPULSION UNIT 3 Sheets-Sheet 3 Filed June 10, 1960 FIG. 3

INVENTOR. WENDELL F. MOORE o ,30

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ATTORNEYJ Unite States Patent C 3,021,095 PROPULSION UNIT Wendell F.Moore, Youngstown, N.Y., assignor, by mesne assignments, to BellAerospace Corporation, Wheatfield, N.Y., a corporation of Delaware FiledJune 10, 1960, Ser. No. 35,315 Claims. (Cl. 244-4) This inventionrelates generally to means for propelling an individual, and pertainsmore particularly to such a means which can be quickly and easilyapplied and which will afford a propelling force to lift the individualfrom the ground and to propel him to a remote spot.

For a number of years, there has been a need for increasing the mobilityof military personnel, for example, infantrymen, by way of providingsome means to directly lift and transport an individual soldier. It isof primary concern in connection with the present invention to providesuch means in the form of a safe, reliable and easily controllablerocket propulsion system having sufficient total impulse to lift andpropel an individual for distances up to approximately two or threemiles.

It is a further object of this invention to provide a device inaccordance with the above which is capable of being utilized by theaverage soldier with an absolute minimum of training.

Another object of this invention resides in the provision of a lightweight rocket propulsion system capable of quick installation andremoval from the individual and which can be safely and easily carriedby one man. To this end, the present invention envisages a simple lightweight harness in the form of a corset upon which is mounted the heaviercomponents of the system so that such heavier components are more easilycarried by the individual inasmuch as the weight thereof is attacheddirectly to and carried by the torso and wherein there is provided acontrol, gas generator, hot gas tube and nozzle assembly pivotallyconnected to the upper extremity of the corset harness and havingseparate means in the form of quickly detachable rings obtaining supportfrom the users shoulders and permitting of kinesthetic control whendesired.

With the above, and other objects in view that will hereinafter appear,the nature of the invention will be more clearly understood by referenceto the following detailed description, the appended claims, and theseveral views illustrated in the accompanying drawings.

FIGURE 1 is a perspective view showing the device as applied to anindividual. b1 FIGURE 2 is a rear elevational view of the assemage.

FIG. 3 is a right side elevational view of the assemblage as shown inFIGURE 2.

FIGURE 4 is a left side elevational view of the assemblage shown inFIGURE 2,

FIGURE 5 is an elevational view partly in section showing details of thegas generator.

FIGURE 6 is an elevational view partly in section showing one of thenozzle members.

Referring at this time more particularly to FIGURE 1, the propulsionunit will be seen to be constructed of two main component parts. Thefirst of these utilizes a corset-like harness 10 by means of which thedevice is directly attached to the users body. Directly carried by thisharness on the back panel thereof are a pair of propellant supply tanks11 and 12 and, intermediate these tanks, a pressurizing gas tank 13 andsuflicient couplings and fittings interconnecting these several tanks aswell as control means therefor later to be described.

- The second of the assemblies includes a pair of hot gas tubes 14 and15 emanating from the gas generator indicated generally by referencecharacter 16, the nozzles 3,021,095 Patented Feb. 13, 1962 indicatedgenerally by the reference characters 17 and 18 at the ends of therespective hot gas tubes, control handle members such as the throttlecontrol assembly indicated generally by the reference character 19 andshoulder engaging rings such as the ring indicated generally by thereference character 20. This entire second component or subassemblage isa rigid, integral unit separate from the first-mentioned component butbeing pivotally attached thereto, in a manner hereinafter morespecifically set forth, permitting a certain amount of freedom ofmovement of the second component relative to the first so that theoperator may, if desired, utilize kinesthetic control,

The harness 10 has an enlarged black panel including the extension 21which projects upwardly behind the users neck so as not only to protectthe user from the heat of the mechanism but also to provide means forpivotally mounting the second component to the harness. As previouslydescribed, there is a propellant supply means which, in the specificform of the invention shown, comprises the two tanks 11 and 12 and thereis also a pressurizing gas supply in the form of the tank 13 which isutilized in the specific example shown to pressurize the tanks 11 and 12and provide the means for discharging the contents of the latter to thegas generator 16.

The tanks 11 and 12 are provided with outlet couplings 25 and 26 havingconnection with branches 27 and 28 of the main line 29 for thepropellant. Also coupled with the main line is a filling valve assembly,indicated generally by reference character 30 having a nipple 31 forconnection to a propellant supply whereby the tanks 11 and 12 may becharged, during which time, of course, the valve 30 is disposed in theopen position through the medium of a handle 32.

The several tanks are rigidly mounted relative to each other by means ofstrap members 33 and 34 having suitable connection directly to theharness 10 and which straps also serve to mount certain component partsof the mechanism. For example, the lower strap 34 mounts a pressureregulating valve 35 and a vent valve 36. The pressurizing gas tank 13 isconnected through line 37, shut-off valve 38, and line 39 to one side ofthe regulator 35, the other side of the regulator being connectedthrough line 40 to the vent valve 36. The vent valve is so constructedas to harmlessly vent the pressurizing gas through the outlet 41 in caseof failure of this part of the system. Leading from the vent valve 36 isa line 42 extending to the manifold block 43 having pressurizing gasbranches 44 and 45 leading therefrom to the respective tops of the tanks11 and 12, as shown.

In the specific form of the invention shown, the propelling medium ishydrogen peroxide and the pressurizing gas is nitrogen. Theaforementioned main line 29 for the propellant, that is, for thehydrogen peroxide, has a discharge branch 46 leading from the main lineto the throttle valve assembly indicated generally by the referencecharacter 47 and on the downstream side of this throttle valve theflexible connection 48 extends to the previously mentioned gas generator16. The throttle valve 47 is provided with an externally projectingactuating rod 49 having a clevis crank 50 fixed thereto havingconnection with a control cable 51 by means of which the How ofpropellant to the gas generator 16 is controlled.

The gas generator is shown in FIGURE 5 and will be seen to include acasing or housing 52 having at its lower end a pair of generallyoppositely directed discharge portions 53 and 54 and having an inlet 55at its upper end. Within the housing 52 are a pair of vertically spacedplates 56 and 57, perforate as shown, and sandwiching therebetween acatalyst bed 58, it being preferred that there is provided below theplate 57 a somewhat enlarged chamber 59 to allow expansion of thegenerated hot gas and distribution thereof evenly to the two dischargebranches 53 and 54. The housing is surrounded by a heat shield 69 havingopenings 61 for cooling, the purpose of the shield being to preventpersonnel from directly contacting the gas generator housing.

1 As can be seen best in FIGURE 2, the hot gas tubes 14 and 15 aredirectly and rigidly connected to the gas generator 16, morespecifically to the branches 53 and 54 thereof, and extend generallylaterally downwardly therefrom. Extending between the two hot gas tubes14 and 15 is a brace or reinforcing member 62 gusseted as at 63 and '64to the gas tubes so thatthe entire structure is rigidly and integrallyformed. The major extent of the gas tubes particularly where they passin close proximity to the user is provided with heat insulative material65 and 66.

As can be best seen in FIGURES l and 3, the shoulder rings 29 arerigidly connected to the gas tubes by means of fore and aft braces 67and 68 so that the shoulder rings too are rigidly and fixedly connectedto the hot gas tubes. The shoulder rings are open at their fronts topermit the assemblage to be easily applied and removed from theindividual and are provided with retaining bars 74) and 71 to hold therings properly in place on the users body. Preferably, these bars arepivotally connected at one end or the other to the shoulder rings, withthe other ends thereof being provided with a suitable quick-releasecoupling or fastening such as a removable pin acting as a latch to holdthese bars in place when desired.

The cross-brace 62 serves, in addition to interconnecting the gas tubes,as a means for pivotally connecting the secondary component to theharness and for this purpose, there is provided a pivot bolt member 75,see particularly FIGURE 1, which pivotally connects the intermediateportion of the cross-brace 62 to the extension 21 of the harness 19. Inthis manner, the operator can, by moving and maneuvering his shoulders,efiect kinesthetic control of the nozzles 17 and 18.

The construction of each nozzle is as is shown in FIGURE 6. Each gastube 14 or is provided with an extension 8% having a ball surface 81provided at the lower extremity thereof mating with a spherical orrather part spherical seat portion 82 of the nozzle body 83 proper. Theinner wall 84 of the nozzle is formed suitably as shown for properdischarge characteristics and the outer wall 85 thereof mounts a pair ofapertured cars 86 and 87 receiving the pivot pins 88 and 89 which passthrough a gimbal ring 90 so as to permit lateral deflection of thenozzles. The gimbal ring is carried by arm projections 91 at either sideof the cover member 92 rigidly affixed to the extensions 80 and thegimbal ring 99 is pivotally connected to these arms by means of pins 93diametrically opposed with respect to each other and completing theuniversal connection between the cover 92 and the nozzle bodies throughthe gimbal ring 90. The nozzle bodies 83 are provided with laterallyoutwardly extending actuator lugs 94 for effecting lateral control ofthe nozzles. Each cover 92 is provided with an inner side extension 96effecting stops to prevent lateral inward deflection of the nozzlestowards the users body. Disposed within each cover 92 is a sealingbellows 97 coupled at its opposite ends by means of rings 98 and 99 tothe extension 80 and the nozzle body 83 respectively, thus sealing theconnection between the ball 81 and its seat 82.

As can be seen best in FIGURE 2, a control spring 100 surrounds each gastube above a respective nozzle assembly, being seated on the shoulders101 of the respective covers 92 and resiliently mounting the bobweightsor stability weights 102 which surround the respective hot gas tubes.Each such weight is provided with a rigid radially projecting arm 103having a rod connection 104 to its respective nozzle lug 94.

The purpose of these weights 102 is to provide stability control for thenozzles operative automatically due to inertia forces and controllingangular acceleration of the system independently of the operatorscontrol although, of course, the control effected by the weights can beoverridden by the manual control means.

In addition to the actuator lugs 94, each nozzle is also provided with afurther actuator lug 95 rigidly connected, in each case, to itsrespective nozzle car 87 (see IGURE 6) and extending upwardly therefromin the region of an associated pivot pin 93. Whereas the actuator lugs94 are provided for the purpose of obtaining lateral outward deflectionof the nozzles, the lugs 95 are utilized for obtaining fore and aftdeflection of the nozzles.

For the purpose of manual control, the lower branch of each shoulderring 20 is provided with an extension, such as those indicated byreference characters 105 and 166. One of such extensions is providedwith a rigid terminal end portion 197 having a pivoted grip lever 198associated therewith so that the operator, by squeezing on the portion163, will actuate the throttle control cable 51. Also, it is preferredthat ,aflight time remaining indicator 109 be mounted on either theextension 105 or they extension 196, in this case, the extension 105,and which issimply a pressure gauge connected to the systemcalibrated inseconds to indicate the flight time remaining inthe system. The otherextension 106 carries a pressure gauge 110 reading in pounds per squareinch. The other extension 186 also has a terminal end portionllluniversally connected thereto and by means of which the deflection ofthe nozzles is controlled, either fore and aft, or laterally, or acombination of both.

For deflecting the nozzles laterally, cables 112 and 113 are providedfor having one end thereof in each case attached to' the bottom ofuniversally pivoted control. handle 111. One cable, 112, extends fromhandle 111 over pulleys 114, 115 and 116 and is connected to arm 103 onthe stabilizing weight 102. The other cable 113 extends from the lowerend of handle 111 over pulleys 117 and'118 on the right hand side and isconnected to the other weight arm 193. Since the nozzles can bedeflected only outwardly in the lateral direction, cables 112 v and 113are adequate inasmuch as tension loads only are required.

For obtaining fore and aft nozzle deflection, handle 111 is providedwith an arm 120 rigid therewith and whichextendszupwardly beyond theuniversal connection between the handle 111 and frame extension 106. Tothe upper end of this arm a Bowden cable 121 is connected which extendsto a junction member 122 from which two separate Bowden cables 123 and124 emanate. Bowden cable 124 extends to lug 95 at the left hand nozzlewhereas cable 123. extends behind the corset as shown in FIG: URE 4 forconnection to the right hand nozzle lug 95. It will be appreciated thatthe Bowden cable system is anchored, where necessary, to achieve bothpush and pull motions of the wire. That is to say, the sheath for themovable wire is appropriately anchored to permit the wire to operateproperly.

That is to say, by virtue of the pivotal connection between the-upperportion of the device (manifold nozzles, etc.) and the harness extension21 and due to the Hexibility of the extension 21, the operator may, bymanipulating his shoulders and/or manipulating the hand grips 107 and111 to deflect the upper portion of the assembly relative to his body,effect disposition of the nozzles so as to propel himself fore and aftas well as laterally. During such manipulation, the operator willinstinctively maintain himself in a generally upright or balanced position, i.e. by swinging his legs, hunching his body, etc. This balancedposition of the operator is made possible by his instinctive shifting ofhis center of gravity, as by the gymnastics as aforesaid. A detailedtreatise of the it deals with a highly sophisticated force system and itwould serve no useful purpose insofar as the present disclosure isconcerned. Suifice it to say it is largely instinctive for the operatorto maintain his upright position while effecting the aforesaid flightcontrol. The same relationship prevails when the nozzles are deflectedto effect control.

What is claimed is:

1. A propulsion unit for an individual such as a foot soldier comprisinga first assembly adapted to be attached to the individuals torso forcarrying the Weightier components of the unit and a second assemblyadapted to be carried by the users shoulders and including propulsionnozzle means, said first assembly including a harness of corset-likeform and having a back panel, and propellant supply and discharge meansattached to said back panel, said second assembly including a gasgenerator having a pair of hot gas tubes emanating therefrom andextending generally in laterally opposite directions from such gasgenerator and each having a downturned end portion mounting a nozzle, ashoulder engaging ring fixed to each gas tube and projecting forwardlytherefrom for engagement with the users shoulders and thereabout, andmanual control means carried by said rings for controlling thedeflection of said nozzles relative to the hot gas tubes and forcontrolling the supply of propellant to said gas generator, saidpropellant supply and discharge means being connected to said gasgenerator.

2. A propulsion unit for an individual such as a foot soldier comprisinga device adapted to be removably attached to a users body, said deviceincluding a torso engaging portion fixedly mounting the weightiercomponents of the unit and thus permitting of the same to be carrieddirectly by the users body and especially by the hips thereof, saiddevice also including an upper portion including propulsion nozzlesprovided with means for attachment to a users shoulders and constitutingthe lighter of the components of the device, the latter portion of thedevice being articulately mounted to the torso engaging portionpermitting of kinesthetic control of said nozzles.

3. A propulsion unit for an individual such as a foot soldier comprisinga first assembly adapted to be attached to the individuals torso forcarrying the weightier components of the unit and a second assemblyadapted to be carried by the users shoulders and including propulsionnozzle means, said first assembly including a harness of corset-likeform and having a back panel, and propellant supply and discharge meansattached to said back panel,

said second assembly including a gas generator having a pair of hot gastubes extending therefrom in generally laterally opposite directionswith each such tube being provided with a down-turned end portionmounting a nozzle pivotally thereon, a shoulder engaging ring fixed toeach gas tube and projecting forwardly therefrom for engagement aboutthe users shoulders, each such ring having a forward extension with oneof such extensions being provided with means for controlling the supplyof propellant to said gas generator, and the other of such extensionsbeing provided with a pivoted hand grip portion connected to saidnozzles for effecting deflections thereof, said propellant supply anddischarge means being connected to said gas generator.

4. The unit as defined in claim 3, wherein said second assembly ispivotally connected to said first assembly to permit of kinestheticcontrol of said nozzles.

5. In a control system of the type having a gas generator, a commonmanifold connected to a gas generator, and a pair of spaced dirigiblenozzles mounted on said manifold an automatic stability device fordamping out undesirable directional deviations of the system, saiddevice comprising a bobweight slidably mounted on said manifold inassociation with each of said nozzles, a spring surrounding said,manifold and seated at its lower end thereon and supporting a respectivebobweight at its upper end, an arm on each of said nozzles extendinglaterally outwardly thereof in a direction opposite the other nozzle ineach case, an arm on each bobweight substantially aligned above the armon the associated nozzle, and a control link extending between each suchpair of aligned arms whereby movement of each bobweight in response todirectional deviations of the system will deflect the associated nozzleangularly outwardly to efliect a restorative counteracting force tostabilize the system.

References Cited in the file of this patent UNITED STATES PATENTS2,007,515 Wunsch et a1 July 9, 1935 2,509,603 Martin May 30, 19502,943,816 Hiller July 5, 1960 FOREIGN PATENTS 923,587 France Feb. 24,1947 OTHER REFERENCES Popular Science, December 1958, page 73. PopularMechanics, vol. 112, July 1959, page 76.

